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    PRESSURE BULKHEAD AND METHOD FOR SUBDIVISION OF AN AIRCRAFT OR SPACECRAFT
    1.
    发明申请
    PRESSURE BULKHEAD AND METHOD FOR SUBDIVISION OF AN AIRCRAFT OR SPACECRAFT 有权
    压力容器和用于分配飞机或间隙的方法

    公开(公告)号：US20100230539A1

    公开(公告)日：2010-09-16

    申请号：US12678723

    申请日：2008-06-18

    Applicant: Stephan Mischereit ,  Andreas Stephan

    Inventor： Stephan Mischereit ,  Andreas Stephan

    IPC: B64C1/10

    CPC classification number: B64C1/10

    Abstract: The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour.

    Abstract translation: 本发明提供一种用于将飞行器或航天器分成内部和外部压力区域的压力舱壁。 压力隔板包括压板，该压板具有与航空器或航天器的内轮廓相对应的边缘，可倾斜地支撑内轮廓上的边缘的支撑装置和将边缘与内轮廓密封的密封件。 本发明的另一方面提供了一种用于将飞行器或航天器细分成内部和外部压力区域的方法。 首先，提供压板，该压板的边缘成形为对应于飞行器或航天器的内轮廓。 在另外的步骤中，边缘可倾斜地支撑在内轮廓上并用内轮廓密封。

    Pressure bulkhead and method for subdivision of an aircraft or spacecraft
    2.
    发明授权
    Pressure bulkhead and method for subdivision of an aircraft or spacecraft 有权
    用于分舱飞机或航天器的压力舱壁和方法

    公开(公告)号：US08444089B2

    公开(公告)日：2013-05-21

    申请号：US12678723

    申请日：2008-06-18

    Applicant: Stephan Mischereit ,  Andreas Stephan

    Inventor： Stephan Mischereit ,  Andreas Stephan

    IPC: B64C1/10

    CPC classification number: B64C1/10

    Abstract: The present invention provides a pressure bulkhead for subdivision of an aircraft or spacecraft into an internal and an external pressure region. The pressure bulkhead comprises a pressure plate having an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft, a supporting means which tiltably supports the edge on the inner contour, and a seal which seals the edge with the inner contour. A further aspect of the invention provides a method for subdivision of an aircraft or spacecraft into an internal and an external pressure region. Firstly, a pressure plate is provided that has an edge shaped so as to correspond to an inner contour of the aircraft or spacecraft. In further steps, the edge is tiltably supported on the inner contour and sealed with the inner contour.

    Abstract translation: 本发明提供一种用于将飞行器或航天器分成内部和外部压力区域的压力舱壁。 压力隔板包括压板，该压板具有与航空器或航天器的内轮廓相对应的边缘，可倾斜地支撑内轮廓上的边缘的支撑装置和将边缘与内轮廓密封的密封件。 本发明的另一方面提供了一种用于将飞行器或航天器细分成内部和外部压力区域的方法。 首先，提供压板，该压板的边缘成形为对应于飞行器或航天器的内轮廓。 在另外的步骤中，边缘可倾斜地支撑在内轮廓上并用内轮廓密封。

    Method for producing a composite skin in the field of aeronautics and astronautics
    3.
    发明授权
    Method for producing a composite skin in the field of aeronautics and astronautics 有权
    在航空和航天领域生产复合皮肤的方法

    公开(公告)号：US09314875B2

    公开(公告)日：2016-04-19

    申请号：US12602459

    申请日：2008-05-15

    Applicant: Andreas Stephan

    Inventor： Andreas Stephan

    IPC: B23P11/00 ,  B21D53/88 ,  B23K26/24 ,  B21J15/00 ,  B21J15/14 ,  B23K15/00 ,  B23K20/12 ,  B23K26/26 ,  B64C1/06 ,  B64C1/12

    CPC classification number: B23K26/24 ,  B21J15/00 ,  B21J15/142 ,  B23K15/0006 ,  B23K20/122 ,  B23K26/26 ,  B23K2101/18 ,  B23K2103/10 ,  B64C1/069 ,  B64C1/12 ,  Y02T50/43 ,  Y10T29/49966 ,  Y10T29/49968 ,  Y10T428/12

    Abstract: A composite skin for the aeronautics and astronautics industries, and also a method for producing a composite skin of this type is provided. The method comprises the following method steps: removing excess material from a butt plate to form a butt strap at one end thereof, subsequently connecting the other end of the butt plate to a skin plate with a substance-to-substance bond, and then fastening a further skin plate to the butt strap to form the composite skin. The idea behind the invention involves replacing a rivet connection with a substance-to-substance bond. This provides the advantage that the weight of the composite skin and the production costs for the composite skin are reduced.

    Abstract translation: 提供了一种用于航空和航天工业的复合皮肤，以及一种生产这种复合皮肤的方法。 该方法包括以下方法步骤：从对接板去除多余的材料以在其一端形成对接带，随后将对接板的另一端连接到具有物质 - 物质粘合的表皮板，然后紧固 一个进一步的皮肤板到对接带形成复合皮肤。 本发明的想法涉及用物质与物质之间的接合来更换铆钉连接。 这提供了复合皮肤的重量和复合皮肤的生产成本降低的优点。

    Structure, especially a fuselage structure of an aircraft or a spacecraft
    4.
    发明授权
    Structure, especially a fuselage structure of an aircraft or a spacecraft 有权
    结构，特别是飞机或航天器的机身结构

    公开(公告)号：US08366043B2

    公开(公告)日：2013-02-05

    申请号：US12740880

    申请日：2008-10-31

    Applicant: Andreas Stephan

    Inventor： Andreas Stephan

    IPC: B64C1/00

    CPC classification number: B64C1/10

    Abstract: The present invention provides a fuselage structure (1; 1′) of an aircraft comprising an annular skin segment (2; 2′) which has a cross-sectional opening (3; 3′), a pressure cap (4; 4′) for a pressure-tight closure of the cross-sectional opening (3; 3′), and a plurality of tension struts (7, 8, 9; 7′, 8′, 9′) which in each case connect the pressure cap (4; 4′) to the annular skin segment (2; 2′) and absorb loads acting on the pressure cap (4; 4′), as tensile loads. This advantageously means that the tension struts (7, 8, 9; 7′, 8′, 9′) do not have to absorb substantially any bending moments. Consequently, the tension struts can be produced with a relatively small cross section, which entails a reduction in weight. Furthermore, it is possible to produce and mount tension struts (7, 8, 9; 7′, 8′, 9′) of this type in a simple manner.

    Abstract translation: 本发明提供一种飞行器的机身结构（1; 1'），其包括具有横截面开口（3; 3'），压力盖（4; 4'）的环形皮肤段（2; 2'）， 用于横截面开口（3; 3'）的压力密封，以及多个张力支柱（7,8,9; 7'，8'，9'），其在每种情况下连接压力盖（ 4; 4'）连接到环形皮肤部分（2; 2'）并吸收作用在压力帽（4; 4'）上的负载作为拉伸载荷。 这有利地意味着张力支柱（7,8,9; 7'，8'，9'）不必基本上吸收任何弯曲力矩。 因此，张力支柱可以以相对小的横截面产生，这需要减轻重量。 此外，可以简单地制造和安装这种类型的张紧支柱（7,8,9，7'，8'，9'）。

    STRUCTURAL COMPONENT AND METHOD FOR STIFFENING AN EXTERNAL SKIN
    7.
    发明申请
    STRUCTURAL COMPONENT AND METHOD FOR STIFFENING AN EXTERNAL SKIN 有权
    结构组分和刺激外部皮肤的方法

    公开(公告)号：US20100237195A1

    公开(公告)日：2010-09-23

    申请号：US12678732

    申请日：2008-06-10

    Applicant: Andreas Stephan

    Inventor： Andreas Stephan

    IPC: B64C1/12 ,  B21D53/88

    CPC classification number: B64C1/12 ,  Y10T29/49622

    Abstract: The present invention provides a structural component for an aircraft or a space craft having an outer skin and a first reinforcing element which runs on the outer skin along a first spatial direction. A second reinforcing element runs over the first reinforcing element in a second spatial direction. A foot element supports the second reinforcing element on the outer skin, the foot element having a feed-through opening in which the first reinforcing element is held in a positive manner. From another point of view, a method is provided for reinforcing an outer skin of an aircraft or space craft, in which a first reinforcing element is attached to the outer skin along a first spatial direction. A foot element having a feed-through opening is attached over the first reinforcing element such that the first reinforcing element is held positively in the feed-through opening. A second reinforcing element is attached to the foot element in a second spatial direction over the first reinforcing element.

    Abstract translation: 本发明提供一种用于飞机或航天飞机的结构部件，其具有外皮和沿第一空间方向在外皮上延伸的第一加强元件。 第二增强元件在第二空间方向上延伸超过第一加强元件。 脚部元件支撑外皮上的第二加强元件，脚元件具有馈通开口，第一加强元件以正向方式保持在该通孔中。 从另一观点出发，提供了一种用于加强飞行器或太空飞船的外皮的方法，其中第一加强元件沿着第一空间方向附接到外皮。 具有馈通开口的脚元件附接在第一加强元件上，使得第一加强元件被正确地保持在馈通开口中。 第二增强元件在第一增强元件上的第二空间方向上附接到脚元件。

    TRANSVERSE SPLICING PLATE FOR CREATING A FUSELAGE, AND A METHOD FOR CONNECTING TWO, IN PARTICULAR WOUND, CFP FUSELAGE SECTIONS
    8.
    发明申请
    TRANSVERSE SPLICING PLATE FOR CREATING A FUSELAGE, AND A METHOD FOR CONNECTING TWO, IN PARTICULAR WOUND, CFP FUSELAGE SECTIONS 有权
    用于创建熔接的横向分隔板，以及用于连接两个，特别是CFP熔融部分的方法

    公开(公告)号：US20100237194A1

    公开(公告)日：2010-09-23

    申请号：US12740183

    申请日：2008-10-30

    Applicant: Andreas Stephan

    Inventor： Andreas Stephan

    IPC: B64C1/06 ,  B21D53/88

    CPC classification number: B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49346 ,  Y10T29/49622

    Abstract: A transverse splicing plate for producing a fuselage of an aircraft by connecting several CFP fuselage sections that have in particular been produced in the winding method, in each case by forming a transverse seam, wherein the flexible transverse splicing plate is of a multilayer construction, in other words it comprises a multitude of plate segments arranged one above the other, wherein each of the plate segments comprises a multitude of longitudinal slits, each being able independently of each other to make small radial bending movements in order to cause tolerance compensation in radial direction between the fuselage sections to be joined, in which tolerance compensation a sliding movement between the sub-plates of the plate segments arranged one above the other takes place in axial direction of the barrel-shaped fuselage sections, and wherein on the inside the ends of the fuselage sections comprise chamfers; as well as a method for producing a connection between two CFP fuselage sections, which have preferably been produced in the winding method, by means of a transverse splicing plate according to the invention.

    Abstract translation: 一种横向拼接板，用于通过连接几个特别是以卷绕方式生产的CFP机身部分，在每种情况下通过形成横向接缝来生产飞行器的机身，其中柔性横向拼接板是多层结构， 换句话说，它包括一个彼此上下布置的多个板段，其中每个板段包括多个纵向狭缝，每个纵向狭缝彼此独立地进行小径向弯曲运动，以便在径向上进行公差补偿 在要连接的机身部分之间，其中公差补偿在一个彼此上下布置的板段的子板之间的滑动运动沿着筒形机身部分的轴向方向发生，并且其中在内侧的 机身部分包括倒角; 以及用于通过根据本发明的横向拼接板来生产优选以卷绕方法制造的两个CFP机身部分之间的连接的方法。

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